What are components does any Helicopter fuselages have?

Major assemblies of a Single-Rotor Helicopter

CABIN

COCKPIT

COCKPIT DOOR

PASSENGER DOOR

INTEGRAL FUEL TANK

BAGGAGE COMPARTMENT

TAIL CONE

HORIZONTAL STABILIZER

VERTICAL STABILIZER

BATTERY AND ELECTRICAL COMPARTMENT

ENGINE COMPARTMENT

TRANSMISSION COMPARTMENT

FLIGHT CONTROL ENCLOSURE

ELECTRONIC COMPORTMENT

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SCRAMJET Engine

• The wall of Ramjet will tend to fail at the higher temperature around 2500k,
• Like Turbojets, Conventional ramjets are also limited by material problem at high Mach Number.
• When the temperature of the air entering the combustor is too high, during which the fuel injected, it will be decomposed by the higher temperature instead been burned (Fuel will absorb rather than producing energy).
• The engine will become a Drag producing machine instead for a Thrust producing device.
• When the air flow is decrease by the scramjet the relative velocity and kinetic energy both decrease, during that energy required that any missing kinetic energy will reappear as internal energy.
• When the flight Mach number exceeds about 6 led to decelerate the flow to subsonic speeds.

Advantage

• No moving parts easies to manufacture.

• Has less weight and simple design.

• Does not have to carry oxygen tank.

• High seed could be achieved easier, so cheaper access to outer space in the future.

Disadvantage

• Scramjet cannot produce efficient thrust unless achieves high speed, around Mach 5.

• Testing a Scramjet design requires a expensive equipments (hypersonic test chambers and launching vehicles).

• Lack of strength.

 

 

 

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Computational Fluid Dynamics

                The art of replacing the partial differential equations of fluid flow with number, this number is spaced and time to obtain a final numerical description of the complete flow field of interest.

The fluid flow is governed by Three Fundamental Principle:

• Mass is conserved

• F = ma (Newton’s 2 law)

• Energy is conserved

Equation most general form is in PDF

Role of CFD

• Round off errors are compromises to get the accuracy in CFD RESULT.
• To carry out numerical experiments help study the fundamental characteristics of the flow. These numerical are directly analogous to actual laboratory experiments.

Types of fields handled by CFD

• Flow field over the space shuttle

• Flow over wing body

• Unsteady, Oscillating flow through supersonic engine inlets

• Flow field over an automobile

• Flow through supersonic combustion ramjet engine

Flow fields cannot be computed by CFD

• Turbulence model

• Chemically reacting flow

      

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Salient Features Of Scramjet Engine And Its Applications For Hypersonic Vehicles

        The scramejet uses a slightly modified Brayton Cycle to produce power, similar to that used for both the classical ramjet and turbine engine. Where Air is compressed and the  fuel injected, mixed and burned to increase the air, the combustion products are Temperature and Pressure then these combustion products are expanded.

For Turbojet engine Air is mechanically compressed by combustor using a turbine. In principle the ramjet and scramjet works the same. Where the forward motion of the vehicle compresses the air then the Fuel injected into the compressed air and burned. Results the high pressure combustion products expand through the Nozzle. Elevating the surface pressure and moving the vehicle forward.

Parts of Scramjet Engine

Scramjet Engine

        Scramjet is a variation of a Ramjet Engine, It is a type of Air breathing Engine where the combustion takes place in subsonic airflow, Scramjet  is supersonic throughout the entire engine , Scramjet operate more effective at extreme high speed of about Mach 5.

Parts of Scramjet Engine

• Inlet

• Isolator

• Combustor

• Nozzle

 

        The different Part of a Scramjet engine is Inlet, Isolator, Combustor and Nozzle. The scramjet engine must be integrated with the Fuselage of the aircraft, specially the air inlet and the Nozzle. Part of the forebody aircraft fuselarge makes the function of air let compressing the freestream air, and the after body acts as a nozzle expanding the gases for the combustion.

Salient Features of Liquid Propellant Rockets

  

Salient Features of Liquid Propellant Rockets:

                A liquid propellant propulsion system is commonly called rocket engines. It has all the hardware components and propellants necessary for its operations for producing thrust.

Liquid propellant propulsion system

Consists of one or more thrust chambers, one or more tanks to store propellants, a feed mechanism to force the propellants from the tanks into the thrust chamber, power source to furnish the energy for the feed mechanism, suitable plumbing or piping or piping to transfer the liquids,

Has a structure to transmit the thrust force, and control devices to initiate and regulate the propellant flow and thus the thrust.

In some application an engine may also include a thrust vector control system, various instrumentation and residual propellant (trapped in pipes, valves, or wetting tanks).

It does not include hardware for non-propulsive purpose, such as aerodynamic surface, guidance, or navigation equipment, or useful payload such as scientific space exploration package or missile warhead.

Ramjet Engines

 

Ramjet Engines in Fighter Aircraft

            Ramjet Engines is a type of Combustion Engine, comes under the category of Air breathing engine. It is the simplest of all the air breathing engines. It consists of a Diffuser, Combustion chamber and a Nozzle, and ramjets do not need any moving parts such as compressors and consequently no turbine as well.

Major Assemble of Ramjet Engines

• Diffuser

• Combustion Chamber

• Nozzle

• Ramjet Engines mechanism are less complicated jet engine for producing thrust in flying vehicle.

• Ramjet Engines are most efficient when operated at supersonic speeds.

• All the compression is occurs in the intake diffuser section producing rise in the static pressure.

• When the air decelerated from a high mach number to a low subsonic mach number, it results in substantial increase in pressure and temperature so the ramjet does not need Compressor and Turbine.

 

Working

• Ramjet produces power by increasing the momentum of the moving fluid by induction of energy by combustion of fuel, so the momentum of the exhaust jet greater and exceed that of the incoming air on continuous cycle.

• Where the Fuel is burned the high pressure air and the mixture is then expanded to ambient static pressure through a Nozzle System.

• High pressure gas expanded through the Nozzle by converting the low subsonic flow in the combustion chamber into a supersonic jet.

• The combine mixture of air and fuel (supersonic jet) exhausted through the C-D Nozzle.

Working cycle of Ramjet Engines

source:NPTL

Types of Jet Engines used in Aircraft

 

What are the Types of Jet Engines used in Aircraft?

Turbofan Engine

Turboprop Engine

Turbojet Engine

Turboshaft Engine

Ramjet Engine

Scramjet Engine

Unmanned Aerial Vehicles (UAV)

Unmanned Aerial Vehicles (UAV)

                After the Wright brothers worked so hard to put humans in the air by flying machines, now a day’s some aerospace engineers are working hard to take out of the flying machine. UAV Unmanned Aerial Vehicles are the Airplanes that have no humans on board which are operated and flown remotely by pilots.

Israel is the first nation to use UAV in the combat situation arguing that loss of relative inexpensive UAV was better than the loss of a pilot and a multi-million dollar airplane.

UAV are mainly used to carry sensors, target designated and electronic transmitters

 Designed to destroy enemy’s target, UAV are more effective fly at greater range and endurance.

Range – Is the maximum distance an aircraft can fly between takeoff and landing.

Endurance – Is the maximum length of time that an aircraft can spend in cruising flight (level flight).

Engine Mounts

        Engine mount is frame structures that support the engine and connect it to the fuselage. Which are designed to distribute the weight of the engine and distribute torque and vibration generated by the engine, Vibration that originated in the reciprocating engine are transmitted through the engine mount to the airplane structure for such mounts engine must be attached with some sort of rubber bushing between the engine and mount attachment to control these vibration. 

Maximum vibration from the engines are controlled when tightened so that the engines move slightly with respect to the rubber bushing which limits in a torsion during operating condition, But at the same time if the bolt are too tight the mount structure will tend to vibrate along engine which would transmitted to Airplane wing and fuselage structure which would be undesirable. To avoid over tighten of bolts the technicians should always refer to the manufacture’s service before tightening such bolts.

Material Used

Engine Mount should withstand waste heat released from the engine and ability to carry heavy engines at temperature of up to 500 ⁰ C base on the requirement three alloys types are used

Nickel-Based alloys: Can withstand high extreme temperature

Titanium alloys:  half the weight of steel, used in the place where the light weight material is needed

Steel alloys: Use at the place where high strength needed at very low temperature.

Based On Aircraft

Light Aircraft - Engine mounts made of welded-steel tubing or aluminium alloy sheet metal.

Turbine powered Aircraft - Engine mounts made of forged metal bolted to airframe.

Design and Types

Engine mounts vary widely in appearance and Construction, but basic features of construction are same. Each aircraft differs from other, heat released from the engine differs base on this criteria each new engine mount should also be unique and to be designed that engine and its accessories should be easy for inspection and maintenance.

Most aircraft which exactly from same manufacturer of the engine shall uses the same mount.

Types

Dynafocal engine mount

Protects the vibration and motion from the engine to be transmitted to aircraft structure, Fixing is based on the centre of gravity of the engine.

Shape: Ring-like

Bolt Point: Usually Four points

 

Conical mount

Conical mount are attached parallel to the firewalls, easy for installation simple and easy to fix to aircraft.

Bolt Point: Usually Four points

Drawbacks: Vibration and Torque are transmitted through the Frames

 

Bed mount

Bed mount are attached under the crankcase, which totally differs from the other type of mount (Conical mount and Dynafocal engine mount), Designed for perfect fitting of the engine avoid transmit vibration to the structure

Bolt Point: Usually Four points in modern aircraft

Vibration is more Danger to Aircraft leads to failure, Engine Mount Helps to avoid some sort of Vibration to be transmitted to Aircraft Structure.

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Control Surface of airplane

Control Surface of airplane

              Control surface of Aircraft is an aerodynamic device mean by which pilot stabilize aircraft and controls the direction and altitude of an aircraft on flight. Control surface is a movable surface which is lighter in construction has light  spar rod at the front edges to provide strength and rigidity, the spar connect the ribs and covered by the thin skinned sheet. The tabs are attached to the trailing edge of the control surface additional device will be attached based of purpose the control surface is used for transmission of tab loads to the surface.

Sheet Materials used in Control Surface

1. Metal structure                   -        Covered with metal skin
2. Composite Structure          -        Covered with fabric
3. Wooden Structure              -        Covered with Plywood or fabric

Drilling

The hole on the surface made using drain holes to prevent water  trapped inside the structure , which causes the control surface to be thrown out of balance

Jointing

Process involved in jointing the components includes fasteners like adhesive and bonding agents.

Flight Control Surface are sub branched into

• Primary Control Surface
• Secondary Control Surface

Primary Control Surface is designed to provide adequate response to controlling device giving a natural feel.

At low speed control will be smooth and sluggish

At high speed control will become increasingly firm

Responding to speed

At low speed the aircraft respond slow to control applied

At high speed the aircraft respond more rapid (faster) to control applied

Primary Control Surface includes:

Ailerons - (ROLL) Control motion along longitudinal axis.

Elevator - (PITCH) Control rotational motion along lateral axis.

Rudder  - (YAW) Control motion along Vertical axis.

Secondary Control Surface are use to improve the aircraft performance characteristics and to release the excessive control loads applied.

Secondary Control Surface includes:

Wing flaps - Used to increase the Lift and Drag increase while Take off.

Slats - Located on the leading edge of the wings. Creates enough lift at high Angle of attack.

Slots - Span wise gap present at each wing allowing air to flow between the wings, which creates lift thus reduces stall.

Trim tabs - Connect trailing edge to large Control Surface, Used to Stabilize the aircraft.

Balance tabs - Control loads on the control surface is significantly reduced, makes aircraft easy to fly.

Anti-Balance tabs - Maintain the stability in the desire position.

Servo tabs - Small Hinged device to assist the movement of the control surface.

The Combination of this Control Surface of Aircraft helps the pilot in controlling and stressing the aircraft during flight .

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